本文選題：旋翼　切入點(diǎn)：新型槳尖　出處：《航空動(dòng)力學(xué)報(bào)》2016年01期 　論文類型：期刊論文

【摘要】：為研究不同形式的新型槳尖在抑制旋翼跨聲速特性方面的作用,開展了多種槳尖對(duì)旋翼局部流動(dòng)及氣動(dòng)特性影響的數(shù)值分析研究.發(fā)展了基于高效嵌套網(wǎng)格方法的旋翼流場(chǎng)高精度CFD求解方法.在此基礎(chǔ)上,詳細(xì)分析了槳尖外形對(duì)旋翼槳葉跨聲速區(qū)域激波強(qiáng)度、激波誘導(dǎo)氣流分離、槳尖渦尾跡及氣動(dòng)性能的影響.數(shù)值結(jié)果表明:槳尖的后掠和上反在緩解旋翼跨聲速特性方面的作用相對(duì)較小;槳尖前掠和下反能更有效地減少槳尖外端跨聲速區(qū)域,降低該位置激波強(qiáng)度并緩解激波-附面層干擾誘導(dǎo)的氣流分離;后掠槳尖在減小旋翼反扭矩方面的整體效果良好,直線前掠槳尖在大槳盤拉力狀態(tài)能夠更有效降低旋翼扭矩(直線前掠30°時(shí),扭矩降低達(dá)12.3%),槳尖下反可以有效抑制槳尖渦強(qiáng)度(拋物下反30°時(shí),槳尖渦強(qiáng)度降低50%),并加快槳尖渦尾跡的耗散.
[Abstract]:In order to study the role of different types of propeller tips in suppressing the transonic characteristics of rotor, Numerical analysis of the effects of various propeller tips on the local flow and aerodynamic characteristics of rotor is carried out. A high precision CFD method for solving rotor flow field based on efficient nested grid method is developed. The shock intensity and shock induced flow separation of rotor blade in transonic region are analyzed in detail. The numerical results show that the tip swept back and back have relatively little effect on the transonic characteristics of the rotor, and the tip forward and downward inversion can effectively reduce the transonic region of the outer tip of the propeller tip, the numerical results show that the tip of the propeller tip has relatively little effect on the transonic characteristics of the rotor rotor, and that the tip forward and downward sweep can reduce the transonic region of the rotor tip more effectively. Reducing the intensity of shock wave at this position and relieving the separation of airflow induced by shock wave and boundary layer interference, the swept back propeller tip has a good overall effect in reducing the reverse torque of rotor. Linear swept forward tip can reduce rotor torque more effectively in the condition of large propeller disc pull (when linear forward swept 30 擄, torque decreases by 12.3g), the tip vortex strength can be effectively suppressed under propeller tip (when parabolic reverse is 30 擄), The intensity of tip vortex is reduced by 50% and the dissipation of tip vortex wake is accelerated.
【作者單位】： 南京航空航天大學(xué)航空宇航學(xué)院直升機(jī)旋翼動(dòng)力學(xué)國(guó)家級(jí)重點(diǎn)實(shí)驗(yàn)室;
【基金】：國(guó)家自然科學(xué)基金(11272150) 江蘇高校優(yōu)勢(shì)學(xué)科建設(shè)工程
【分類號(hào)】：V211.52

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本文編號(hào)：1562607